The indicial admittance of a pointed wing, bounded by two supersonic leading edges and a straight trailing edge and located in an otherwise uniform supersonic flow, is calculated on the basis of linearized theory. This result is applied to the calculation of the lift and moments on a wide delta airfoil due to a sudden change of angle of attack, a uniform, sharp-edged gust, an impulsive gust, and sharp-edged and impulsive gusts having antisymmetric linear velocity distributions over the span. The response of a two-dimensional airfoil to an impulsive gust is also calculated. These results are given in the form of algebraic formulas and curves.